Publication: Thermodynamics and aerodynamics analysis of blading system of an aerobased gas turbine
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Date
2002-03-01
Authors
Abd. Rahim, Rosilawati
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Abstract
A two stage gas turbine is required to be designed from a standard aero-jet engine
for the generation of electricity. The gas turbine in it’s is most common form is a heat
engine operating by means of a series of process consist of compression of air taking from
atmosphere, increase of gas temperature by the constant pressure combustion of fuel in the
air, expansion of the gasses to the external atmosphere the whole being a continuous flow
process. The aspect have been taken in the design as follow:
An analysis of aerodynamics aspects.
An analysis of thermodynamics aspects.
Blade and root analysis.
Disc analysis
Shaft and bearing analysis.
This project consist of 4 chapters which is
Chapter 1
-In this chapter consist of introduction to the gas turbine, thermodynamics cycle of Brayton
with explained the ideal cases, and the component of the gas turbine which is compressor,
combustor and turbine.
Chapter 2
-In this chapter explained more on turbojet, turboprop and turbofan. But it is more details
on turbojet which is consist of thermodynamics analysis and including the formula of the
turbojet process.
Chapter 3
-In this chapter consist of the calculation of the blade, root, disc, and shaft.
Chapter 4
-In this chapter consist of summary and conclusion.